临近空间飞行器纵向逆控制系统设计

Longitudinal inversion control system design for near-space vehicle

建立了临近空间飞行器无动力滑翔阶段的纵向运动模型,并应用动态逆方法推导了模型的逆系统。系统相对阶等于绕质心运动模型的系统阶数,实现了绕质心运动模型的线性化。为了克服纵向运动模型的隐动态和参数的不确定性,在内环动态逆控制器的基础上,设计了外环最优调节器。仿真结果表明:飞行器纵向逆控制系统可以准确跟踪俯仰角或攻角指令,并对参数不确定性和外界干扰具有较好的鲁棒性,具有工程适用性。

Near-space glide vehicle motion was modeled by nonlinear longitudinal dynamic equations. The Inverse system of this model was obtained by using dynamic inversion approach. The relative degree of dynamic model was equal to the rotational motion system order, so rotational motion dynamic model could be Input/Output linearization completely. The dynamic inversion method and optimal control were used in inner-loop and outer-loop for the longitudinal dynamic model. Simulation studies demonstrate that the proposed controller tracks the pitch angle or angle of attack command accurately, meets the performance requirements with acceptable control inputs and is robust with respect to the parametric uncertainties and external disturbance.